Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
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Debivarati Sarangi
Abstract
Understanding the occurrence of various feedback mechanisms of an under-expanded impinging supersonic jet is a crucial task in research. The presence of several jet modes is examined in this study for the flat and corrugated impinging plate geometries. The behavior of impinging plate configurations during mode switching is investigated by varying the flow state, such as the jet Mach number. The staging behavior at various jet Mach numbers is observed using acoustic spectral plots and schlieren flow visualization. To explore the presence of various types of modes during the jet impingement due to the modification of jet Mach number, ensemble averaging and Proper Orthogonal Decomposition of schlieren images are carried out. In the majority of situations, the corrugated design shows a reduction in tonal noise and overall sound pressure level. In exceptional cases, for the corrugated plates, the enhanced overall sound pressure level is caused by the existence of axisymmetric instability (A1, A2).
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Research ethics: The work does not involve any animal studies and such ethical issues are not applicable.
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Author contributions: Debivarati Sarangi: Conceptualization, Experimental investigation, Methodology, Formal analysis, Visualization, Data curation, Validation, Writing – original draft; Ramanujam Karthik: Experimental investigation, post processing of Experimental data, Visualization, Data curation; Kothandaraman Srinivasan: Conceptualization, Writing – review & editing, Supervision.
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Competing interests: The authors declare that they have no known competing financial interests or personal relationships that could have appeared to influence the work reported in this paper.
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Research funding: None.
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Data availability: The raw data can be obtained on request from the corresponding author.
Nomenclature (SI units)
- M j
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Jet Mach number
- d
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diameter of the jet (mm)
- h
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Non dimensional Standoff distance
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Articles in the same Issue
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
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- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
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Articles in the same Issue
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
